XFOIL Version 6.94 Calculated polar for: Eif385mod 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.008 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- -3.000 -0.0720 0.05307 0.03383 -0.0158 0.9993 1.0007 -2.750 -0.0683 0.05173 0.03207 -0.0171 0.9993 1.0007 -2.500 -0.0445 0.05141 0.03094 -0.0207 0.9993 1.0007 -2.250 -0.0164 0.05166 0.03031 -0.0233 0.9993 1.0007 -2.000 0.0104 0.05213 0.03004 -0.0249 0.9993 1.0007 -1.750 0.0352 0.05271 0.02999 -0.0256 0.9993 1.0007 -1.500 0.0583 0.05336 0.03010 -0.0258 0.9993 1.0007 -1.250 0.0800 0.05406 0.03035 -0.0256 0.9993 1.0007 -1.000 0.1006 0.05482 0.03073 -0.0254 0.9993 1.0007 -0.750 0.1202 0.05565 0.03124 -0.0250 0.9993 1.0007 -0.500 0.1389 0.05654 0.03188 -0.0245 0.9993 1.0007 -0.250 0.1568 0.05752 0.03263 -0.0240 0.9993 1.0007 0.000 0.1739 0.05859 0.03353 -0.0236 0.9993 1.0007 0.250 0.1900 0.05977 0.03458 -0.0232 0.9993 1.0007 0.500 0.2052 0.06108 0.03579 -0.0228 0.9993 1.0007 0.750 0.2192 0.06253 0.03718 -0.0225 0.9993 1.0007 1.000 0.2319 0.06416 0.03877 -0.0224 0.9993 1.0007 1.250 0.2433 0.06599 0.04059 -0.0223 0.9993 1.0007 1.500 0.2531 0.06805 0.04265 -0.0224 0.9993 1.0007 1.750 0.2614 0.07034 0.04494 -0.0227 0.9993 1.0007 2.000 0.2684 0.07283 0.04745 -0.0231 0.9993 1.0007 2.250 0.2750 0.07551 0.05011 -0.0237 0.9993 1.0007 2.500 0.2814 0.07827 0.05287 -0.0244 0.9993 1.0007 2.750 0.2881 0.08107 0.05564 -0.0252 0.9993 1.0007 3.000 0.2952 0.08386 0.05840 -0.0261 0.9993 1.0007 3.250 0.3030 0.08663 0.06112 -0.0270 0.9993 1.0007 3.500 0.3114 0.08936 0.06381 -0.0279 0.9993 1.0007 3.750 0.3202 0.09207 0.06647 -0.0288 0.9993 1.0007 4.000 0.3296 0.09477 0.06913 -0.0297 0.9993 1.0007 4.250 0.3393 0.09745 0.07178 -0.0306 0.9993 1.0007 4.500 0.3493 0.10011 0.07441 -0.0315 0.9993 1.0007 4.750 0.3597 0.10277 0.07704 -0.0324 0.9993 1.0007 5.000 0.3702 0.10542 0.07967 -0.0333 0.9993 1.0007